Rigid bar for electrically connecting a machine in an aircraft turbine engine

- SAFRAN AIRCRAFT ENGINES

Disclosed is an electrically conductive rigid bar (80) for electrically connecting an electric machine (70) of an aircraft turbine engine, characterised in that it comprises: —an elongate body (80a) made from electrically conductive material having a polygonal cross-section greater than or equal to 50 mm2, and— an electrical insulation sheath (80b) that surrounds the body, at least one of the longitudinal ends (84a) of the body not being covered by the sheath and comprising a through-hole (86) in which a bolt (88) for fastening and electrically connecting this end is mounted.

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Description
TECHNICAL FIELD OF THE INVENTION

The present invention relates to an electrically conductive rigid bar for the electric connection of an electric machine in an aircraft turbomachine, as well as to a method for maintaining said turbomachine.

TECHNICAL BACKGROUND

The prior art comprises in particular the documents FR-A1-2 842 565, FR-A1-2 896 537 and FR-A1-2 922 265, which describe turbomachines equipped with electric machines. The prior art also comprises the document WO-A1-2017130733.

The aeronautical world is now asking many questions about the relevance of using hybrid engines for commercial aviation. The use of electrical energy is now considered not only to meet the functions of the aircraft but also to electrify the functions of the turbomachine.

This observation leads to the study of hybrid engine architecture solutions, combining fossil energy of the fuel and electrical energy to ensure the driving of the propulsion portion (fan of the turbomachine) and the feeding of certain engine and/or aircraft functions.

These architectures can in particular be based on a high bypass ratio and reducer type architecture, but also on a multiple body architecture (2 or 3). In these architectures, the turbomachine comprises a low-pressure body and a high-pressure body, each body comprising a shaft connecting a rotor of a compressor to a rotor of a turbine.

It is known to equip an aircraft turbomachine with an electric machine. We recall that an electric machine is an electromechanical device based on the electromagnetism allowing the conversion of electrical energy into work or mechanical energy for example. This process is reversible and can be used to produce electricity.

Thus, depending on the final use of a machine, we use the terms of:

    • generator to designate an electric machine producing electrical energy from a mechanical energy,
    • motor for an electric machine producing a mechanical energy from an electrical energy.

An electric machine can also behave in motor mode as well as in generator mode.

The integration of a high-power electric machine on the low-pressure body of a turbomachine, in particular of the high bypass ratio type, is very complex. Several installation areas are possible but the advantages and the disadvantages of each are numerous and diverse (problem of mechanical integration of the machine, temperature resistance of the machine, accessibility of the machine, etc.).

One solution to this problem would be to integrate the electric machine directly downstream of the fan of the turbomachine. However, one difficulty would be the connection of this machine to the power electronic circuit which is usually located at a distance from the machine.

The use of power harnesses would pose some technical problems in this environment. The large diameter harnesses have very large bending radii, which would not be compatible with this environment. The integration of harnesses would require supports to limit the transmission of vibrations to the surrounding parts and their damage.

The present invention proposes a solution to at least some of the problems discussed above.

SUMMARY OF THE INVENTION

The invention proposes an assembly for an aircraft turbomachine, comprising an electric machine of annular shape, at least one electrically conductive rigid bar for electrically connecting the electric machine comprising:

    • a body made of an electrically conductive material with an elongated shape and a polygonal cross-section greater than or equal to 50 mm2, and
    • an electrical insulation sheath which surrounds said body,

at least one of the longitudinal ends of the body not being covered by the sheath and comprising a through orifice in which is mounted a bolt for attaching and electrically connecting this end, and an electric harness for connecting a stator of the machine to the bar, the electric harness comprising an end equipped with a lug which is applied and tightened on said end of the bar, by means of said bolt.

The present invention therefore proposes a solution to the problem of electric connection of an electric machine in an aircraft turbomachine. This connection is ensured by one or more rigid bars and not just electric harnesses. The bar can be shaped to have relatively small radii of curvature. In addition, it is rigid and not very prone to vibrations during operation. Finally, it does not necessarily require any particular attachment means, unlike the harnesses of the prior art. The assembly according to the invention also comprises a harness for connecting the electric machine to the bar, which provides a greater flexibility of connection.

The assembly according to the invention may comprise one or more of the following characteristics, taken alone from each other, or in combination with each other:

    • the body has a cross-section greater than or equal to 100 mm2;
    • the body or the bar has a length between 100 and 500 mm;
    • the body has a substantially rectangular cross-section;
    • the cross-section of the body is constant; this allows to ensure a continuity of the electric flow;
    • the body is twisted so that one of its longitudinal ends extends in a first plane P1, and the other of its longitudinal ends extends in a second plane P2 substantially perpendicular to the first plane P1;
    • the bar is generally L-shaped or S-shaped.

The invention also proposes an aircraft turbomachine, comprising at least one electrically conductive rigid bar comprising a body made of an electrically conductive material with an elongated shape and a polygonal cross-section greater than or equal to 50 mm2, and an electrical insulation sheath which surrounds said body, at least one of the longitudinal ends of the body not being covered by the sheath and comprising a through orifice in which is mounted a bolt for attaching and electrically connecting this end or an assembly as described above.

The turbomachine may comprise:

    • a gas generator having a longitudinal axis,
    • a fan located at an upstream end of the gas generator and configured to rotate about said axis, and
    • an electric machine with a generally annular shape which is mounted coaxially downstream of the fan, and which comprises a rotor rotatably coupled to the fan, and a stator connected by said bar (80) to a power electronic circuit,

the fan being configured to generate a main gas flow, a portion of which flows into a primary annular duct of the gas generator to form a primary flow, and another portion of which flows around the gas generator to form a secondary flow,

the primary duct being delimited by a first and a second annular envelopes coaxial with the gas generator, the primary duct being passed through by guide vanes, referred to as IGV, for connecting the first and second envelopes, as well as by tubular arms of an inlet casing located downstream of the IGV,

the gas generator comprising a third annular envelope of the gas generator which coaxially surrounds the second envelope,

the second and third envelopes being connected together at their upstream ends to form an annular splitter nose for separating the primary and secondary flows.

The present invention thus proposes a solution for the integration of an electric machine, a first advantage being linked to the fact that in the integration area of this machine, ideally directly downstream of the fan and thus upstream of the compressor or the compressors, the temperatures prevailing there are relatively low and thus optimal for this machine. The rotor of the machine is driven by the fan and is therefore at a relatively low speed, in particular if the turbomachine comprises a reducer. In addition, the machine is located as close as possible to the flow ducts of the flows and has a relatively large diameter and can therefore produce significant power compared to the machines of the prior technologies.

The turbomachine according to the invention may comprise one or more of the following characteristics, taken in isolation from each other, or in combination with each other:

    • said end of the bar is an upstream end of the bar which is located within the first envelope, substantially in line with said IGV and/or said splitter nose;
    • the turbomachine comprises a nacelle casing extending around the gas generator and delimiting around the latter a secondary annular flow duct of the secondary flow, the secondary duct being passed through by guide vanes, referred to as OGV, for connecting the nacelle casing to said third annular envelope, the OGV preferably being located downstream of the IGV and substantially in line with the tubular arms of the inlet casing;
    • the IGV are connected to sectors of the first, second and third envelopes, so as to form sectorized segments removable independently from each other;
    • the longitudinal end of the bar is covered and protected by at least one insulation cover fitted and attached on a flange of the gas generator, which is for example the attachment and support flange of the electric machine.

The present invention further relates to a method for maintaining a turbomachine as described above, comprising the steps consisting in:

    • disassembling and removing at least one of the sectorized segments, in particular at the level of said bar,
    • optionally, disassembling and removing the insulation cover,
    • unscrewing and removing the bolt to disengage the bar, and
    • removing the electric machine.

The invention also relates to an electrically conductive rigid bar for the electric connection of an electric machine of aircraft turbomachine, characterised in that it comprises:

    • a body of electrically conductive material with an elongated shape and a polygonal cross-section greater than or equal to 50 mm2, and
    • an electrical insulation sheath that surrounds said body,

at least one of the longitudinal ends of the body not being covered by the sheath and comprising a through orifice in which is mounted a bolt for attaching and electrically connecting this end.

The present invention therefore proposes a solution to the problem of electric connection of an electric machine in an aircraft turbomachine. This connection is ensured by one or more rigid bars and not just electric harnesses. The bar can be shaped to have relatively small radii of curvature. In addition, it is rigid and not very prone to vibrations during operation. Finally, it does not necessarily require any particular attachment means, unlike the harnesses of the prior art.

The bar according to the invention may comprise one or more of the following characteristics, taken alone or in combination with each other:

    • the body has a cross-section greater than or equal to 100 mm2;
    • the body or the bar has a length between 100 and 500 mm;
    • the body has a substantially rectangular cross-section;
    • the cross-section of the body is constant; this allows to ensure a continuity of the electric flow;
    • the body is twisted so that one of its longitudinal ends extends in a first plane P1, and the other of its longitudinal ends extends in a second plane P2 substantially perpendicular to the first plane P1;
    • the bar has a general L or S shape.

BRIEF DESCRIPTION OF FIGURES

The invention will be better understood and further details, characteristics and advantages of the invention will become apparent from the following description made by way of non-limiting example with reference to the attached drawings, in which:

FIG. 1 is a schematic view in axial cross-section of an aircraft turbomachine with a high bypass ratio and reducer;

FIG. 2 is a partial schematic half-view in axial cross-section of an aircraft turbomachine according to the invention equipped with an electric machine;

FIG. 3 is similar to FIG. 2 and shows an electric connection bar from a stator of the machine to a power electronic circuit,

FIG. 4 is a schematic perspective view of a portion of the turbomachine of FIG. 2 and shows in particular one end of the electric connection bar,

FIGS. 5a to 5e are views of a detail of FIG. 3 and illustrate steps of a method for maintaining the turbomachine,

FIG. 6 is a schematic perspective view of a portion of the turbomachine in FIG. 2 and illustrates one of the steps of the method for maintaining the turbomachine,

FIG. 7 is a schematic cross-sectional view of an electric harness, and

FIG. 8 is a schematic cross-sectional view of an embodiment of an electric connection bar.

 DETAILED DESCRIPTION OF THE INVENTION

First, reference is made to FIG. 1, which schematically represents a double-body and double-flow aircraft turbomachine 10.

The turbomachine 10 conventionally comprises a gas generator 12, upstream of which is arranged a fan 14. The fan 14 is surrounded by a casing 16 which is surrounded by a nacelle 18 that extends around and along a major portion of the gas generator 12.

The gas generator 12 here comprises two bodies, namely a low-pressure body 12a or LP and a high-pressure body 12b or HP. Each body comprises a compressor and a turbine.

The terms “upstream” and “downstream” are considered along a main direction F of flow of the gases in the turbomachine 10, this direction F being parallel to the longitudinal axis A of the turbomachine.

From upstream to downstream, the gas generator 12 comprises a low-pressure compressor 20, a high-pressure compressor 22, a combustion chamber 24, a high-pressure turbine 26 and a low-pressure turbine 28.

The fan 14 comprises an annular row of vanes 30 driven in rotation by a fan shaft 32 which is connected to the rotor of the low-pressure body 12a by means of a reducer 33. The gas flow passing through the fan (arrow F) is separated upstream of the gas generator 12 by an annular splitter nose 34 into a radially internal annular flow, referred to as primary flow 36 that flows in a primary annular duct of the gas generator 12, and a radially external annular flow, referred to as secondary flow 38 that flows in a secondary annular duct between the gas generator 12 and the nacelle 18 and provides most of the thrust for the turbomachine.

An inlet casing 40 structurally connects the gas generator 12 to the casing 16 and to the nacelle 18. The inlet casing 40 comprises an annular row of radially internal arms 42 extending into the flow duct of the primary flow 36, and an annular row of radially external guide vanes 44, referred to as OGV (acronym for Outer Gear Vane), extending into the flow duct of the secondary flow 38.

The arms 42 are generally limited in number (less than ten) and are tubular and crossed by auxiliaries. These arms 42 have a structural role because they allow the transmission of forces between the bearing supports and the suspensions. They also have a role of passage of the auxiliaries, allowing to make cross the auxiliaries through the duct by fairing them, thus limiting the aerodynamic losses in the duct. These arms do not have a flow straightening function because they have no camber and are not sufficient in number to carry out this function.

The number of guide vanes 44 (OGV) is generally higher than ten. They allow to straighten the flow of the fan thanks to a specific number and camber. They also have a structural function because they support the casing around the fan (fan casing).

The flow duct of the primary flow 36 is further crossed by other guide vanes 52, referred to as IGV (acronym for Inner Gear Vane). The IGV 52 are evenly distributed around the axis A and are located upstream of the inlet casing 40 and more precisely upstream of the arms 42. These vanes allow to straighten the flow coming from the fan when it enters the primary duct. They do not have a structural role. They are in sufficient number (for example more than 10) and with a certain camber to straighten the flow of the fan penetrating the primary duct.

The flow duct of the primary flow 36 is delimited by two coaxial annular envelopes, respectively internal 37a and external 37b. In particular, the IGV 52 and the arms 42 are connected to these envelopes 37a, 37b. The flow duct of the secondary flow 38 is delimited internally by an annular envelope 39 coaxial with the envelopes 37a, 37b, and externally by the nacelle casing 16. The OGV 44 are connected to the envelopes 37b, 39.

Each of the envelopes 37a, 37b, 39 may be formed by several adjacent walls or covers.

The rotor of the low-pressure body 12a as well as the fan shaft 32 are guided upstream by bearings 46, 48 and 50. These bearings 46, 48, 50 are of the ball or roller type and each comprise an internal ring mounted on the shaft to be guided, an external ring carried by an annular bearing support and a roller bearing between the rings.

In a known manner, the reducer 33 is of the epicyclic gear train type and comprises a sun gear centred on the axis A, a ring gear extending around the axis, and planet gears that mesh with the sun gear and the ring gear and are carried by a planet carrier.

In the example shown, the ring gear is stationary and fixedly connected to a support 62 of the bearings 46, 48. The planet carrier is rotatable and coupled to the fan shaft 32. The sun gear of the reducer is coupled by an input shaft 56 to the main shaft 58 of the low-pressure body.

The input shaft 56 is guided by the bearing 50 which is carried by a bearing support 60. The fan shaft 32 is guided by the bearings 46, 48.

The bearing supports 60, 62 extend around the axis A and are stationary parts connected to the stator and in particular to the inlet casing 40.

FIG. 2 is a larger scale, more detailed view of a portion of FIG. 1, and illustrates an embodiment of a turbomachine according to the invention.

The elements of FIG. 2 that have already been described with reference to FIG. 1 are designated by the same references.

In particular, FIG. 2 shows the area Z between the fan disc 32a and the reducer 33, in which an electric machine 70 is installed. Only one support 33a of the ring gear of the reducer 33 is visible in FIG. 2, this element being connected, for example, to the inlet casing 40 or to the bearing support 62.

The cross-section in the drawing in FIG. 2 passes through one of the IGV 52, which may be full. The cross-section passes through an OGV 44 as well as through an arm 42 which is tubular for the passage of auxiliaries, as mentioned above. Each arm 42 comprises upstream an edge 42a and downstream an edge 42d, respectively leading edge and trailing edge of the primary flow 36.

Each arm 42 comprises an internal cavity 42c that is closed radially outward by a wall 44a of the OGV 44. This wall 44a is formed in one part with the OGV 44 and is attached to annular flanges, respectively upstream 43a and downstream 43b, of the inlet casing 40. The cavity 42c is isolated from the auxiliaries by the wall 42b.

The internal cavity 42c of each arm 42 is closed radially inward by an annular wall of the inlet casing 40. At the upstream end of this wall 40a, the inlet casing 40 comprises a radially internal annular flange 40b for attachment of the bearing support 62. At the downstream end of the wall 40a, the inlet casing 40 comprises a radially internal annular attachment flange 40c, for example for attaching an annular gutter for recovering oil sprayed by the reducer 33 by centrifuging.

The reducer 33 as well as the bearings 46, 48, 50 visible in FIG. 1 are located in an annular lubrication enclosure E which is sealed upstream by the bearing support 62 and at least one non-visible seal, and downstream by the bearing support 60 and at least one non-visible seal. The external periphery of the enclosure E is sealed in particular by the wall 40a.

FIG. 2 allows to show that the envelope 37a mentioned above is formed of several successive walls such as the wall 40a and an annular shroud 64 located upstream of the wall 40a and connected to the internal periphery of the IGV 52.

The envelope 37b is formed by several successive walls and in particular an annular shroud 66 located upstream of the inlet casing 40. This shroud 66 extends around the shroud 64 and is connected to the external periphery of the IGV 52.

The envelope 39 is formed of several successive walls such as the wall 44a and an annular shroud 68 located upstream of the wall 44a. This shroud 68 extends around the shroud 66 and the upstream ends of the shrouds 66, 68 are connected together to form the splitter nose 34.

As discussed above, the electric machine 70 is located in an annular area Z, this area Z being delimited here upstream by the fan 14, and in particular the disc 32 for connecting the fan vanes 30 to the fan shaft 32, and downstream by the bearing support 62.

The machine 70 is generally annular in shape and comprises a rotor 70a and a stator 70b. The rotor 70a has a generally annular shape extending about the axis A and is carried by a support element 72 which itself has a generally annular shape.

In the example shown, the support element 72 comprises a cylindrical wall 72a surrounded by the rotor 70a and attached to the internal periphery of the latter. The upstream end of this wall 72a is connected on the one hand to a radially internal annular flange 72b for attachment to the fan disc 32a, and on the other hand, to an external annular rim 72c.

The rim 72c comprises an internal cylindrical surface 72d bearing on an external cylindrical surface of the fan 14 so as to ensure the centring of the rotor 70a. The rim 72c further comprises external annular wipers 72e of a labyrinth type seal.

The stator 70b is also generally annular in shape and is carried by an annular support element 74.

The element 74 comprises an external annular surface 74a which internally defines the flow duct of the gas flow F, between the fan 14 and the splitter nose 34. The element 74 is attached to the external periphery of the stator 70b and comprises an upstream end that cooperates, for example by means of an abradable annular coating, with the aforementioned wipers 72e.

The downstream end of the element 74 is axially aligned with the shroud 64, an upstream peripheral edge of which is axially engaged in an annular groove 74b of the element 74. This groove 74b is oriented axially downstream. The engagement of the upstream edge of the shroud 64 in the groove 74b of the element 74 ensures an overlap and thus avoids a step in the duct which would disturb the flow F.

The downstream end of the element 74 further comprises an annular flange 76 for attaching to the bearing support 62 or to the inlet casing 40. This flange 76 is generally U-shaped in axial cross-section with the opening oriented radially outward. This flange 76 thus defines an annular space X which serves for the electric connection of the stator 70b, as will be described in more detail in the following with reference to FIG. 3 in particular. In the example shown, the flange 76 is attached by screws to a flange of the bearing support 62 and to the flange 40b of the inlet casing.

The element 74 may be formed of a single part, or of two annular and coaxial parts mounted around each other.

One of the particularities of this installation lies in the fact that the electric machine 70 and in particular its stator 70b is located as close as possible to the main flow F after passing through the fan 14. This allows on the one hand to have an electric machine with a large diameter and thus with a higher potential power than the technologies proposed so far, and on the other hand to have a machine which is cooled by the flow F. Advantageously, the thermal rejections of the electric machine are dissipated by this cooling.

For this purpose, the surface 74a swept by the flow F preferably has an aerodynamic profile, as shown in the drawing. The element 74 ensures the heat exchange by thermal conduction between the stator 70b and the flow F.

The stator 70b is connected by electric connection means to a power electronic circuit 78 which is located between the two envelopes 37b, 39 and thus in the gas generator 12.

FIGS. 3 to 6 illustrate an embodiment of these electric connection means which comprise a rigid bar 80.

Although one or more electric harnesses may additionally be used for the electric connection of the stator 70b, at least one rigid bar 80 is used, which provides many advantages.

In a preferred embodiment of the invention, the stator 70b is connected by a first electric harness 82c to one end of the bar 80, the opposite end of which is connected by a second electric harness 82d to the circuit 78. In this case, the cross-section of the core 82a of each harness 82c, 82d is preferably identical or close to the cross-section of the body 80a of the bar 80. The cross-section of the bar 80 and in particular of its body 80a is preferably constant over the entire length of the bar.

The bar 80, visible in its entirety in FIG. 7, is shaped to run from the area Z to the circuit 78. It can have a complex general shape such as L, S, Z, etc.

The bar 80 comprises ends, respectively upstream 84a and downstream 84b, which are exposed, i.e. not covered by the sheath 80b, in order to be able to connect the bar 80 to the harnesses 82c, 82d (FIGS. 4, 5 and 7).

Each of the ends 84a, 84b comprises an orifice 86 for mounting a bolt 88 (screw and nut, or even washer). This bolt 88 is used to attach one end 84a, 84b of the bar 80 to the corresponding harness 82c, 82d, preferably by means of a lug 90. The lug is connected to one end of the harness and comprises a plate intended to be applied to the corresponding end 84a, 84b and to be clamped and attached there by means of the bolt 88 (FIGS. 4 and 5c-5e).

The bar 80 can be twisted, as in the example shown, the bar then comprising one of its ends 84a which extends in a plane P1 (which is the cross-sectional plane of FIG. 3 and which passes through the axis A of the turbomachine) and the other of its ends 84b which extends in a plane P2 perpendicular to the plane P1 (the plane P2 is substantially tangent to a circumference centred on the axis A—FIGS. 3 and 5c).

The invention proposes a particular path for the bar 80 from the stator 70b to the circuit 78, and more particularly between the harnesses 82c, 82d. Note that in practice, the stator 70b may be connected by several bars 80 to the circuit 78. These bars 80 are then preferably evenly distributed around the axis A and each connected by harnesses 82c, 82d to the stator 70b and to the circuit 78. The following description of a bar 80 is therefore applicable to each electric connection bar of the stator of the electric machine to the power electronic circuit.

In the embodiment shown in FIGS. 3 to 6, the bar 80 travels through one of the tubular arms 42 of the inlet casing 40, then along the axis A and an OGV 44.

The bar 80 has a general Z or S shape and comprises:

    • a first end portion 80d comprising the end 84a for connecting to the electric machine 70, this first end portion 80d being located inside the first envelope 37a,
    • a second end portion 80e comprising the end 84b for connecting to the circuit 78, this second end portion 80e being located between the second and third envelopes 37b, 39, and
    • an intermediate portion 80c extending within one of the tubular arms 42 of the inlet casing 40.

The first portion 80d is substantially straight and extends substantially parallel to the axis A from the space X to the interior of the cavity 42c. The end 84a is located in the aforementioned space X and connected by the bolt 88 to the harness 82c in this space X. The first portion 80d passes axially through an orifice 40d in the upstream flange 40b of the inlet casing 40. FIG. 3 shows that the wall 40a extends radially inside the bar 80 and thus inside the orifice 40d to ensure that the cavity 42a is sealed from the enclosure E.

An insulation cover 94a is fitted radially outward from the end 84a and is attached to the flange 40b by screws 95 (FIGS. 5b, 5c and 6). This cover 94a closes the space X and is intended to be surrounded by the shroud 64.

Another insulation cover 94b may be fitted radially inwardly of the end 84a, in the space X. This cover 94b may also be attached to the flange 40b by the screws 95 (FIG. 4, 5c-5e).

The covers 94a, 94b are made of a dielectric material. Their function is to protect the electric connection in the space X, in particular by avoiding the creation of electrical arcs with the neighbouring motor parts.

The intermediate portion 80c is inclined at an angle α in the range of 120-150° relative to the first portion 80d. The portion 80c extends radially outward from upstream to downstream and can follow the inclination of the arm 42 in which it is housed.

The second portion 80e is substantially straight and extends substantially parallel to the axis A, to the circuit 78. To do this, it passes axially through a notch 92 in the downstream flange 43b of the inlet casing 40 (FIG. 3). This is an axial notch 92 formed at the external periphery of the flanges 43b for attaching the OGV 44 and shaped so that the bar 80 can travel through this notch 92 without interfering with the attachment of the arm 44 to the flange 43b. FIG. 5 further allows to show that the end 84b is bent downstream of the flange 43b to be oriented substantially parallel to that flange.

The intermediate portion 80c is inclined at an angle β on the order of 120-150° relative to the second portion 80e.

The shroud 64 is integral with the radially internal ends of the IGV 52. Its upstream end comprises the edge 64a engaged in the groove 74b, and its downstream end comprises an edge 64b bearing axially against a cylindrical shoulder of the inlet casing 40 or of its flange 40b.

The shroud 66 is integral with the radially external ends of the IGV 52. Its upstream end is connected to the upstream end of the shroud 68 to form the splitter nose 34, as discussed above. The downstream ends of the shrouds 66, 68 are also connected together to form an annular flange 79 for attaching by screws or the like to the inlet casing 40.

From FIGS. 3, 5a and following, it can be seen that the shrouds 64, 66 and 68 and the IGV 52 form a sectorized annular member here.

Thus, the IGV 52 are connected to sectors of the shrouds 64-68, so as to form sectorized segments removable independently from each other.

FIGS. 5a to 5e and 6 illustrate steps of a method for maintaining the turbomachine 10.

In the order shown of the steps illustrated in FIGS. 5a to 5e, these steps allow a disassembling of the electric machine 70. It is understood that these steps need only to be repeated in reverse order to complete a machine assembly 70.

Prior to the first step shown in FIGS. 5a and 5b, the fan module comprising the fan 14 and the rotor 70a of the electric machine is removed from the rest of the turbomachine, preferably by axial translation upstream.

At least one of the aforementioned sectorized segments, and in particular the one or the ones located in line with the bar 80, is disassembled and removed (FIG. 5b). The screws 95 for attaching the cover 94a are then unscrewed and removed to remove the cover 94a protecting the electric connection located in the space X (FIG. 5c).

The bolt 88 is disassembled and removed, allowing the bar 80 to be disengaged from the harness 82c (FIG. 5d).

The support element 74 integral with the stator 70b of the electric machine can then be disengaged from the bearing support 52 and the inlet casing 40 and removed by translating axially upstream (FIG. 5e).

FIG. 7 shows a cross-section of an electric harness 82 that is generally circular in shape and comprises a conductive core 82a formed by a strand of wires and an insulation external sheath 82b. FIG. 8 shows an example of an embodiment of a bar 80, which comprises a conductive body 80a preferably having a polygonal shape and for example rectangular in cross-section. This cross-section is preferably constant. The bar 80 further comprises an insulation external sheath 80b.

The present invention allows to provide many advantages:

    • the bar 80 allows, contrary to a harness, very short bending radii, which, in the environment concerned, is essential; this allows to limit the thickness of the splitter nose 34 to a thickness close to that of the bar 80; moreover, the “twistable” profile of the bar allows to adapt itself according to the area crossed: radial position (in the plane P1) to enter the arm 42 of the inlet casing 40 and axial position (in the plane P2) at the level of the OGV 44;
    • the bar 80 is rigid, so there is no risk of vibrations due to too much flexibility and therefore no need for specific support in the arms of the inlet casing 40;
    • the path described above is compatible with all the oil auxiliaries circulating in the arms of the inlet casing 40; moreover, the walls of the inlet casing 40, and in particular the walls 40a and 42b, isolate the bar 80 from these oil auxiliaries, which limits the risk of fire;
    • this path avoids the passage of the bar 80 into the oil enclosure E; this avoids adding a seal; and
    • the modularity linked to the ease of assembly/disassembly of the bar 80 by removing only a few parts of the turbomachine.

This invention could be applied to any turbomachine equipped with an electric machine upstream of a structural casing such as an inlet casing or other.

Claims

1. An assembly for an aircraft turbomachine, comprising:

an electric machine of annular shape,
at least one electrically conductive rigid bar (80) for electrically connecting the electric machine comprising: a body made of an electrically conductive material with an elongated shape and a polygonal cross-section greater than or equal to 50 mm2, and an electrical insulation sheath which surrounds said body,
at least one of the longitudinal ends of the body not being covered by the sheath and comprising a through orifice in which is mounted a bolt for attaching and electrically connecting this end, and
an electric harness for connecting a stator of the machine to the bar, the electric harness comprising an end equipped with a lug which is applied and tightened on said end of the bar, by means of said bolt.

2. The assembly of claim 1, wherein the body has a substantially rectangular cross-section.

3. The assembly according to claim 1, wherein the body is twisted so that one of its longitudinal ends extends in a first plane P1, and the other of its longitudinal ends extends in a second plane P2 substantially perpendicular to the first plane P1.

4. The assembly of claim 1, wherein the bar is generally L-shaped or S-shaped.

5. An aircraft turbomachine, comprising at least one electrically conductive rigid bar comprising:

a body made of an electrically conductive material with an elongated shape and a polygonal cross-section greater than or equal to 50 mm2, and
an electrical insulation sheath which surrounds said body, at least one of the longitudinal ends of the body not being covered by the sheath and comprising a through orifice in which is mounted a bolt for attaching and electrically connecting this end.

6. The turbomachine according to claim 5, comprising:

a gas generator having a longitudinal axis,
a fan located at an upstream end of the gas generator and configured to rotate about said axis, and
an electric machine with a generally annular shape which is mounted coaxially downstream of the fan, and which comprises a rotor rotatably coupled to the fan, and a stator connected by said bar to a power electronic circuit,
the fan being configured to generate a main gas flow, a portion of which flows into a primary annular duct of the gas generator to form a primary flow, and another portion of which flows around the gas generator to form a secondary flow,
the primary duct being delimited by a first and a second annular envelopes coaxial with the gas generator, the primary duct being passed through by guide vanes, referred to as IGV, for connecting the first and second envelopes, as well as by tubular arms of an inlet casing located downstream of the IGV,
the gas generator comprising a third annular envelope which coaxially surrounds the second envelope,
the second and third envelopes being connected together at their upstream ends to form an annular splitter nose for separating the primary and secondary flows.

7. The turbomachine according to claim 6, wherein said end of the bar is an upstream end of the bar that is located within the first envelope, substantially in line with said IGV and/or said splitter nose.

8. The turbomachine according to claim 6, wherein it comprises a nacelle casing extending around the gas generator and delimiting around the latter a secondary annular flow duct of the secondary flow, the secondary duct being passed through by guide vanes, referred to as OGV, for connecting the nacelle casing to said third annular envelope, the OGV preferably being located downstream of the IGV and substantially in line with the tubular arms of the inlet casing.

9. The turbomachine according to claim 6, wherein the IGV are connected to sectors of the first, second and third envelopes, so as to form sectorized segments removable independently from each other.

10. The turbomachine according to claim 9, wherein the longitudinal end of the bar is covered and protected by at least one insulation cover fitted and attached on a flange of the gas generator, which is for example the attachment and support flange of the electric machine.

11. A method for maintaining a turbomachine according to claim 9, comprising the steps consisting in:

disassembling and removing at least one of the sectorized segments, in particular at the level of said bar,
optionally, disassembling and removing the insulation cover,
unscrewing and removing the bolt to disengage the bar, and
removing the electric machine.

12. The turbomachine according to claim 5, comprising an annular electric machine and an electric harness for connecting a stator of the machine to the bar, the electric harness comprising an end equipped with a lug which is applied and tightened onto said end of the bar, by means of said bolt.

Referenced Cited
U.S. Patent Documents
11753175 September 12, 2023 Millier
20200169069 May 28, 2020 Hiramitsu et al.
20220403751 December 22, 2022 Millier
20220412267 December 29, 2022 Millier
20230002066 January 5, 2023 Millier
Foreign Patent Documents
3422479 January 2019 EP
2842565 January 2004 FR
2896537 July 2007 FR
2922265 April 2009 FR
3044865 June 2017 FR
3053387 January 2018 FR
2011/161023 December 2011 WO
2017/130733 August 2017 WO
Other references
  • International Search Report received for PCT Patent Application No. PCT/FR2020/052157, dated Jan. 14, 2021, 6 pages (2 pages of English Translation and 4 pages of Original Document).
Patent History
Patent number: 11881754
Type: Grant
Filed: Nov 24, 2020
Date of Patent: Jan 23, 2024
Patent Publication Number: 20230016978
Assignees: SAFRAN AIRCRAFT ENGINES (Paris), SAFRAN ELECTRICAL & POWER (Blagnac)
Inventors: Vincent Francois Georges Millier (Moissy-Cramayel), Loic Paul Yves Guillotel (Moissy-Cramayel), Philippe Delbosc (Moissy-Cramayel)
Primary Examiner: Pedro J Cuevas
Application Number: 17/780,875
Classifications
Current U.S. Class: Combined (415/121.3)
International Classification: H02K 5/22 (20060101); F01D 9/06 (20060101); F01D 15/10 (20060101); H02K 7/18 (20060101); H02K 15/00 (20060101);